JP5572458B2 - Radial inlet guide vanes for combustors - Google Patents

Description

  The present application relates generally to gas turbine engines, and more particularly to use a radial inlet guide vane or swirler in a combustor to provide a more uniform air flow distribution to the combustor nozzle. About that.

  In gas turbine engines, operating efficiency increases as the temperature of the combustion gas stream increases. However, higher gas stream temperatures can generate higher levels of nitrogen oxides (NOx) or emissions, which are subject to both federal and state government regulations in the United States, and are similar overseas. Subject to regulations. Thus, there is a balance between operating the gas turbine in an efficient temperature range and at the same time ensuring that the generation of NOx and other types of emissions remains below regulatory levels.

  Recent combustion concepts involve the use of multiple nozzles with many smaller diameter passages in the combustor rather than several nozzles with larger diameter passages. Nozzles with these small diameter passages provide fast fuel / air mixing within a short flow residence time. The nozzle also provides strong wall heat transfer with effective cooling using fuel and / or air. Thus, these small nozzles or other types of combustion nozzles can have the ability to reduce emissions and further allow the use of highly reactive types of synthesis gas and other fuels, particularly high hydrogen fuels. However, these nozzle designs may require that more of the combustor cap space be utilized to properly distribute air among many small nozzles.

  In order to minimize the possibility of emissions and flashback, it is desirable to make the airflow distribution across the nozzles as uniform as possible. Current combustor designs may have inter-nozzle air flow fluctuations or even inter-passage air flow fluctuations therein. The outermost nozzle or tube may experience less air flow due to local flow separation when air reaches the nozzle. Such delamination can adversely affect nozzle operability as it can cause flame holding and flashback on nozzles with less airflow. Exfoliation can also adversely affect combustion-generated emissions such as nitrogen oxides (NOx) and carbon monoxide (CO). The degree of non-uniform air flow distribution can also vary with load or total air mass flow. In combustor cases with short liners or without liners, the cap surface may be curved to make the nozzle flow slightly inward. However, such a design may require more air near the outer diameter region when supplying the flow.

WILLY STEVE ZIMINSKY, et al., Title: Premixed Direct Injection Nozzle, filed on Feb. 4, 2009, and assigned USSN: 12 / 365,382.

  Thus, there is a desire to provide a more uniform air flow distribution around the combustor and combustor cap. Preferably, such a uniform air flow uses both highly reactive synthesis gas, high hydrogen fuel and similar types of fuels to both reduce emissions and improve overall performance of the gas turbine engine. Should be possible.

  The present application thus provides a combustor. The combustor includes an internal flow path penetrating the combustor, several nozzles communicating with the internal flow path, and an inlet guide disposed around the internal flow path to form a swirl flow in the internal flow path. And a wing system.

  The present application further provides a combustor. The combustor includes an internal flow path penetrating the combustor, a premixed direct injection nozzle communicating with the internal flow path, and a number of swirling flows disposed in the internal flow path. And an inlet guide vane.

The present application further provides a combustor. The combustor includes an internal flow path penetrating the combustor, a cap member, several nozzles disposed in the cap member and in communication with the internal flow path, and some disposed around the internal flow path. Inlet guide vanes. Inlet guide vanes, and a partial non-swirling flow terminates at around extending from the lower portion of the flow passage can be formed partially swirling flow and the flow passage window in forming the entire swirl flow It is possible to have a substantially uniform distribution among the nozzles.

  These and other features and improvements of the present application will become apparent to those skilled in the art upon review of the following detailed description, taken in conjunction with the several drawings and claims.

1 is a side cross-sectional view of a gas turbine engine that can use a combustor as described herein. FIG. FIG. 2 is a side cross-sectional view of a combustor can with several bundled multiple tube injection nozzles of the gas turbine engine of FIG. 1. 1 is a side cross-sectional view of a combustor can with an inlet guide vane system as described herein. FIG. FIG. 4 is a side cross-sectional view of a combustor can equipped with the inlet guide vane system of FIG. 3. The top view of a combustor can provided with the inlet guide blade system of FIG.

  Referring now to the drawings wherein like reference numerals represent like elements throughout the several views, FIG. 1 shows a side cross-sectional view of a gas turbine engine 10. As is known, the gas turbine engine 10 may include a compressor 12 that pressurizes the incoming air stream. The compressor 12 delivers a pressurized air flow to the combustor 14. The combustor 14 mixes the pressurized air stream with the pressurized fuel stream and ignites and burns the mixture. (Although only a single combustor 14 is shown, the gas turbine engine 10 may include any number of combustors 14.) Next, hot combustion gases are delivered to the turbine 16. The hot combustion gases drive the turbine 16 to produce mechanical work. The mechanical work produced in the turbine 16 drives the compressor 12 and drives an external load such as a generator.

  The gas turbine engine 10 may use natural gas, various other types of syngas, and other types of fuel. The gas turbine engine may be a 7F or 9F type high power gas turbine engine commercially available from General Electric Company, Schenectady, NY. The gas turbine engine 10 may have other configurations and may use other types of components. Other types of gas turbine engines may be used herein. A plurality of gas turbine engines 10, other types of turbines, and other types of power generation devices may be used together herein.

  FIG. 2 is a side cross-sectional view of an example of a combustor 14 that can be used herein. Combustor 14 includes a combustor can 15 that extends from an end cover 18 disposed at a first end thereof to a cap member 20 at an opposite end thereof. The cap member 20 is spaced from the end cover 18 to form an internal flow path 22 for the flow of pressurized air through the combustor can 15. The cap member 20 may form a premixed direct injection nozzle 23 or other type of fuel nozzle or injector extending therethrough. The premix direct injection nozzle 23 may include a number of small nozzles 24 in communication with the fuel passage 25. The small nozzles 24 can be arranged at an inclination, or the small nozzles 24 can be arranged straight. The fuel passage 25 extends from the end cover 18 to the fuel nozzle 23 and can supply fuel to the fuel nozzle 23. The premixing injection nozzle 23 generally provides good fuel air mixing with low combustion generation NOx and low fuel pressure loss to achieve high system efficiency.

  The combustor 14 further includes a combustion liner 26 and a flow sleeve 28 disposed upstream of the combustor can 15. Combustion liner 26 and flow sleeve 28 may form an outer flow path 30 that extends through combustor can 15 and in reverse flow communication with internal flow path 22. The outer flow path can cool the combustion liner 26.

  Thus, air from the compressor 12 flows through the outer flow path 30 between the combustion liner 26 and the flow sleeve 28 and then reverses into the combustor can 15. The air then flows through an internal flow path 22 formed between the end cover 18 and the cap member 20. As air flows through the premixed direct injection nozzle 23 of the cap member 20, the air is mixed with the fuel flow from the fuel passage 25 and ignited in the combustion chamber 32. The combustor 14 shown herein is only an example. Many other types of combustor 14 designs and combustion methods may be used herein.

  When the air flow reaches the nozzle 23 of the cap member 20 through the internal flow path 22, a large speed distribution fluctuation may occur over the cap member 20. These speed fluctuations are particularly problematic when using several premixed direct injection nozzles 24 with a large number of small diameter tubes 24, rather than each using a small number of known large nozzles. There is a possibility. Such speed fluctuations can adversely affect emissions levels and other types of combustion dynamics as described above. These speed fluctuations may increase from the outer diameter region 34 of the cap member 20 toward the central region 36.

  3-5 illustrate a side cross-sectional view of a combustor 100 as may be described herein. The combustor 100 can include a combustor can 110 similar to that described above. Combustor 100 may include an inlet guide vane system 120 disposed within the combustor. The inlet guide vane system 120 can act as a flow regulator and can be disposed around the outer flow path 30 between the combustion liner 26 and the flow sleeve 28. The inlet guide vane system 120 can be attached to the end cover 18 or otherwise positioned.

The inlet guide vane system 120 may include a number of guide vanes 130, each guide vane 130 being arranged radially on the axis 140 and rotating with the axis 40. Guide vanes 130 may be disposed around the lower portion 150 of the flow passage 160 through the combustion liner 26. Guide vanes 130 may terminate in the longitudinal direction in the window 170 of the flow Re passage 160 in the upper part (close to the end cover 18) of the flow passage 160. Area ratio of the window 170 of the flow passage 160 which is not provided with a guide vane 130 and lower portion of the flow passage 160 with a number of guide vanes 130, so as to achieve a desired air flow distribution between the downstream nozzle Can be changed. The angle of the guide vanes 130 can be fixed or adjustable. Any number or shape of guide vanes 130 can be used. The shaft 140 can be attached to the drive motor or otherwise powered.

During use, the air flow 190 can travel along the outer flow path 30 and can flow into the internal flow path 22 through the guide vane system 120 and toward the small nozzle 23 of the cap member 20. The guide vanes 130 can create a specific swirl angle that forms the swirl flow 200 at a higher pressure near the outer diameter region 34 of the cap member 20. The strength of the swirl flow 200 can be controlled by changing the swirl angle and / or length of the guide vanes 130. Accordingly, a transfer function can be established between the guide vanes 130 and the air flow rate that ensures a substantially uniform air distribution across the cap member 20 and nozzle 23 in both full and partial load conditions. The total length and chord length along with the swirl angle of the guide vanes 130 can be optimized to provide a more uniform air form distribution across the nozzle 24. Furthermore, the inlet guide vanes 130 may be formed at least partially swirling flow, whereas, window flow passage 160, to form a partially non-swirling flow, the entire resulting swirling flow 200 is nozzle 24 Can have a more uniform distribution.

  Accordingly, the inlet guide vane system 120 forms a low pressure drop and variable swirl regulator that provides a uniform air flow distribution between the nozzles 24 under all load conditions. The inlet guide vane system 120 allows such uniform air distribution even when the short liner 26 is used in high hydrogen fuel combustion.

  The foregoing description relates only to some embodiments of the present application, and in this specification, those skilled in the art will depart from the general technical idea and technical scope of the present invention defined by the claims and their equivalents. It should be understood that many changes and modifications can be made without

DESCRIPTION OF SYMBOLS 10 Gas turbine engine 12 Compressor 14 Combustor 15 Combustor can 16 Turbine 18 End cover 20 Cap member 22 Internal flow path 23 Premixing direct injection nozzle 24 Small diameter tube nozzle 25 Fuel path 26 Combustion liner 28 Flow sleeve 30 Outer flow path 32 combustion chamber 34 outside diameter region 36 central region 100 combustor 110 combustor cans 120 inlet guide vane system 130 inlet guide vanes 140 shaft 150 lower portion 160 flow passage 170 window <br/> 180 driving motor 190 air flow 200 swirling flow

Claims (10)

A combustor (100), the combustor (100) being
An internal flow path (22) passing through the combustor;
A plurality of fuel nozzles (24) in communication with the internal flow path (22), the plurality of fuel nozzles (24) extending in the axial direction and spaced apart from each other in the radial direction ;
Includes upstream in disposed around said internal passage (22) swirling flow to the internal flow path and the inlet guide vane system (120) to form a (200) of said plurality of fuel nozzles (24) The inlet guide vane system (120),
A plurality of windows (170) disposed circumferentially upstream of the plurality of fuel nozzles (24);
A plurality of inlet guide vanes (130) disposed in the circumferential direction upstream of the plurality of fuel nozzles (24), the plurality of inlet guides disposed in proximity to each of the plurality of windows (170). With wings (130)
A combustor (100). The combustor (100) of claim 1, wherein an angle of the plurality of inlet guide vanes (130) is adjustable. Wherein the plurality of inlet guide vanes (130), Ru extends from the lower portion of the flow passage (160) (150), according to claim 1 or claim 2 wherein the combustor (100). The combustor (100) of claim 3 , wherein the area ratio between the lower portion (150) of the flow passage (160) and the window (170) of the flow passage (160) can be varied.
The each of the plurality of inlet guide vanes (130) is disposed on a shaft (140) attached to a drive motor and can be rotated with the shaft. Combustor (100). The combustor (100) according to any preceding claim , further comprising an end cover (18), wherein the inlet guide vane system (120) is mounted about the end cover (18). . Further comprising a combustion liner (26) and a flow sleeve (28) forming an outer flow path (30) through the combustor, wherein the inlet guide vane system (120) comprises the outer flow path (30) and the internal flow. The combustor (100) according to any one of the preceding claims , disposed between the passages (22). It further includes a cap member (20) with an outer diameter region (34) and a central region (36), wherein the swirling flow (200) is substantially uniformly distributed over the outer diameter region (34) and the central region (36). A combustor (100) according to any one of the preceding claims , comprising: The combustor (100) of any preceding claim , wherein the plurality of fuel nozzles (24) includes a plurality of small diameter tube nozzles (24). The combustor (100) according to any of the preceding claims , wherein the inlet guide vane system (120) acts as a flow regulator.

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